Gas turbine nozzle with a flow groove

Abstract

The present application provides a turbine nozzle. The turbine nozzle may include an airfoil with a leading edge and a trailing edge and a flow groove extending from the leading edge to the trailing edge.

I claim: 
     
       1. A turbine nozzle, comprising:
 an airfoil extending from a base to a tip, wherein the tip of the airfoil is inclined along a rotor axis; 
 the airfoil comprising a leading edge and a trailing edge; and 
 a flow groove extending inwardly from a suction side surface of the airfoil such that the flow groove has a depth measured from the suction side surface of the airfoil, the flow groove substantially parallel to the tip of the airfoil; 
 the flow groove extending from the leading edge to the trailing edge only along the suction side of the airfoil; 
 wherein the flow groove blends into the suction side surface at the leading edge and the trailing edge of the airfoil, such that a first depth of the flow groove at either the leading edge or the trailing edge of the airfoil is less than a second depth of the flow groove along the side of the airfoil. 
 
     
     
       2. The turbine nozzle of  claim 1 , wherein the flow groove is positioned adjacent to the tip. 
     
     
       3. The turbine nozzle of  claim 1 , wherein the flow groove comprises a substantial V-like shape. 
     
     
       4. The turbine nozzle of  claim 1 , wherein the flow groove extends in a substantially linear direction. 
     
     
       5. The turbine nozzle of  claim 1 , wherein the turbine nozzle comprises a last stage nozzle. 
     
     
       6. The turbine nozzle of  claim 1 , further comprising a plurality of flow grooves. 
     
     
       7. The turbine nozzle of  claim 1 , wherein the flow groove is shaped to reduce flow migration in a flow of hot combustion gases along the airfoil. 
     
     
       8. A turbine, comprising:
 a plurality of nozzles; and 
 a plurality of buckets; 
 the plurality of buckets comprising an airfoil; 
 the airfoil extending from a base to a tip, wherein the tip of the airfoil is inclined along a rotor axis, the airfoil comprising a leading edge, a trailing edge, a suction side and a flow groove extending only along the suction side of the airfoil between the leading edge and the trailing edge; 
 wherein the flow groove extends inwardly from the suction side of the airfoil such that the flow groove has a depth measured from the suction side of the airfoil, the flow groove substantially parallel to the tip of the airfoil; and 
 the flow groove blends into the suction side at the leading edge and the trailing edge of the airfoil, such that a first depth of the flow groove at either the leading edge or the trailing edge of the airfoil is less than a second depth of the flow groove along the suction side of the airfoil. 
 
     
     
       9. The turbine of  claim 8 , wherein the flow groove is positioned adjacent to the tip. 
     
     
       10. The turbine of  claim 8 , wherein the flow groove comprises a substantial V-like shape. 
     
     
       11. The turbine of  claim 8 , wherein the flow groove extends in a substantially linear direction. 
     
     
       12. The turbine of  claim 8 , further comprising a plurality of flow grooves. 
     
     
       13. The turbine of  claim 8 , wherein the flow groove is shaped to reduce flow migration in a flow of hot combustion gases along the airfoil. 
     
     
       14. A turbine nozzle airfoil, comprising:
 an airfoil extending from a base to a tip, wherein the tip of the airfoil is inclined along a rotor axis, the airfoil comprising:
 a leading edge; 
 a trailing edge, 
 a pressure side; 
 a suction side; and 
 a flow groove extending from the leading edge to the trailing edge only along the suction side; 
 
 wherein the flow groove extends inwardly from the suction side of the airfoil such that the flow groove has a depth measured from the suction side of the airfoil, the flow groove substantially parallel to the tip of the airfoil; and 
 the flow groove blends into the outer surface at the leading edge and the trailing edge of the airfoil, such that a first depth of the flow groove at either the leading edge or the trailing edge of the airfoil is less than a second depth of the flow groove along the suction side of the airfoil. 
 
     
     
       15. The turbine nozzle airfoil of  claim 14 , wherein the flow groove is positioned adjacent to the tip. 
     
     
       16. The turbine nozzle airfoil of  claim 14 , wherein the flow groove comprises a substantial V-like shape.